JP2001288554A - Repairing material, method for repairing heat resisting alloy member, and hot zone parts repaired by the method - Google Patents

Abstract

PROBLEM TO BE SOLVED: To obtain a repairing material for repairing the cracks and wall- thickness loss of a heat resisting alloy member having controlled crystal structure, e.g. a member made of unidirectionally solidified alloy or single crystal alloy, particularly a γ'-strengthened type heat resisting alloy member, to obtain a method for repairing a heat resisting alloy member, by which the resultant repaired part can be provided with a crystal-structure-controlled structure equal to that of the heat resisting alloy member and properties equal to those of the heat resisting alloy member, and also to obtain hot zone parts repaired by the method. SOLUTION: The repairing material 3 is used for repairing the defective part, such as cracks and wall-thickness loss, of the heat resisting alloy member 1 having controlled crystal structure, particularly a γ'-strengthened type Ni-base alloy member. The repairing material 3 has a composition composed essentially of Ni and containing, by weight, <=6.0% Cr and 1.0-3.5% B.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a repair material for repairing, in particular, a .gamma .'- strengthened Ni-based alloy, in which the crystal structure used for a gas turbine or the like is controlled to be unidirectional or single crystal, and this material is used. The present invention relates to a method for repairing a heat-resistant alloy member used and a technique relating to a high-temperature component repaired by the method.

[0002]

2. Description of the Related Art As a technique for repairing a moving blade and a stationary blade of a gas turbine, which is a high-temperature component, an alloy powder having a composition equivalent to that of a heat-resistant alloy member as a material of the blade, a heat-resistant alloy member, There is known a technique of injecting a paste obtained by kneading a component having the same composition and lowering the melting point, for example, an alloy powder containing B or Si in an organic binder, and then heating the mixture in vacuum to melt and solidify the brazing material ( Product name: ADH,
It is called TURBOFIX or the like. ).

[0003] In addition, for a defect having a large area generated in a heat-resistant alloy member, a sheet obtained by solidifying the above two kinds of alloy powders with an organic binder is applied to the defect portion, and the material is melt-solidified by vacuum heat treatment to build up. It has been known.

In addition to this technique, a method of repairing a defect in a heat-resistant alloy member has been developed. An alloy powder having a composition equivalent to that of the heat-resistant alloy member is coated on the repaired portion by a thermal spraying method to build up the portion. Repair technology is disclosed in
No. 0442. In this method, a technique using high-speed gas spraying (HVOF) as a thermal spraying method is disclosed in Japanese Patent Application Laid-Open No. 8-284606.

[0005] By using a technique as described above to fill and repair a crack or a defect generated in a high-temperature component such as a wing with a repair material, it is possible to reduce the further propagation of the crack and the thinning of the defect. It is possible.

[0006]

However, in the conventional method for repairing a heat-resistant alloy member as described above, although a repair material is filled in a defective portion such as a crack, the crystal structure is controlled to be unidirectional or single crystal. When repairing a heat-resistant alloy member, the crystal structure of the repaired part does not become the same as the crystal structure of the heat-resistant alloy member, so that the properties of the repaired part are greatly different from those of the heat-resistant alloy member. .

That is, a heat-resistant alloy having a controlled crystal structure, such as a directionally solidified alloy or a single crystal alloy, particularly γ ′ (Ni
Repair materials for repairing cracks and thinning of heat-resistant alloy members made of ₃ (Al, Ti)) reinforced Ni-based heat-resistant alloys have not been known in the past.

The present invention has been made to solve such a problem, and repairs cracks and thinning of a heat-resistant alloy member having a controlled crystal structure, particularly a γ′-reinforced Ni-base heat-resistant alloy member. The purpose of the present invention is to provide a repair material for performing the repair.

Further, the repair part has a controlled crystal structure equivalent to that of the heat-resistant alloy member, and a method for repairing a heat-resistant alloy member having the same characteristics as the heat-resistant alloy member and a high-temperature part repaired by the method are provided. With the goal.

[0010]

Means for Solving the Problems In order to achieve the above object, the present inventors have conducted various studies.

In a conventional polycrystalline alloy, the alloy composition is N
i or Co as the main component, Cr content of 8-30% and B
And those containing about 0.01 to 5% of Si are known. However, when the repair material is filled and heated in order to repair the heat-resistant alloy member with a controlled crystal structure using the repair material of the conventional composition, the repaired material is melted and solidified, and the repaired defect is repaired. It was found that many crystal grain boundaries were generated and the structure was changed to a structure having a different crystal orientation as compared with the heat-resistant alloy member. As a result of intensive studies on the factors, the present inventors found that Cr,
The inventors have found that there is a correlation between the amounts of B and oxygen and the easiness of formation of crystal grain boundaries, and have reached the present invention.

That is, the invention according to claim 1 is a repair material for repairing a defective portion such as a crack or a thinning of a heat-resistant alloy member having a controlled crystal structure, particularly a γ′-reinforced Ni-based alloy member. The repair material is composed mainly of Ni and C
It is characterized by containing at most 6.0% by weight of r and 1.0 to 3.5% by weight of B.

Cr is a component necessary for maintaining corrosion resistance. B is used for lowering the melting point of the heat-resistant alloy member and for preferentially melting the repair material without melting a large amount of the heat-resistant alloy member. It is an element to be added. In the present invention, by using a repair material in which the amounts of Cr and B added are adjusted, it is possible to prevent the generation of microcrystals that hinder the crystal structure due to the generation of grain boundaries during melting and solidification of the repair material, Since the solidification behavior in a state where the structure is extended is easily obtained, a crystal structure close to that of the heat-resistant alloy member can be obtained.

According to a second aspect of the present invention, there is provided a repair material for repairing a defective portion such as a crack or a reduced thickness of a heat-resistant alloy member having a controlled crystal structure, particularly a γ′-reinforced Ni-based alloy member, This repair material is characterized by containing Ni as a main component, containing up to 5.0% by weight of Cr, 1.5 to 3.0% by weight of B, and 0.1% by weight or less of oxygen.

In the present invention, the amount of oxygen in the repair material should preferably be small not only to reduce the generation of grain boundaries but also to reduce the formation of oxides in the repaired portion. Since the reduction is accompanied by difficulty, the upper limit of the oxygen content is preferably set to 0.1% by weight.

A third aspect of the present invention is a method of repairing a heat-resistant alloy member having a controlled crystal structure, particularly a defect-resistant portion such as a crack or thinning of a γ′-reinforced Ni-base heat-resistant alloy member. Then, the repaired surface where this defect exists
Is contained at most 6.0% by weight of B and 1.0 to 3.5% by weight of B, and is coated with a repair material mainly composed of Ni, and then heated in an inert atmosphere.

The invention according to claim 4 is a method of repairing a heat-resistant alloy member having a controlled crystal structure, particularly a defect-resistant portion such as a crack or thinning of a γ′-reinforced Ni-base heat-resistant alloy member. The repaired surface where this defect exists is
As a main component, up to 5.0% by weight of Cr, and 1.5 to 1.5% by weight of B.
After coating with a repair material containing 3.0% by weight and oxygen at 0.1% by weight or less, heat treatment is performed in an inert atmosphere.

In the present invention, after the repair material is coated on the defective portion, the repair material can be permeated into the defective portion by performing a heat treatment in an inert atmosphere.

According to a fifth aspect of the present invention, after a component made of a material equivalent to a heat-resistant alloy member and processed into a shape conforming to the size of a defective portion is loaded into the defective portion, the defective portion and the defective portion are removed. 5. The method for repairing a heat-resistant alloy member according to claim 3, wherein a repair material is coated on a gap between the component and the component, and a heat treatment is performed in an inert atmosphere.

When the size of the defective portion is large, the heat-resistant alloy member can be efficiently repaired in a short time by loading a component made of the same material as the heat-resistant alloy member into the defective portion as in the present invention. It is.

According to a sixth aspect of the present invention, a mixture of an alloy powder having the same composition as the heat-resistant alloy member and the repair material according to the third or fourth aspect is used as the repair material. 6. A method for repairing a heat-resistant alloy member according to any one of 3 to 5.

In the present invention, as the repair material, a mixture of an alloy powder having the same composition as that of the heat-resistant alloy member and a repair material whose composition is adjusted may be used. In this case, the repair material portion mainly has a crystal structure equivalent to that of the heat-resistant alloy member. However, since B also diffuses into the alloy powder of the heat-resistant alloy member, the diffusion progresses quickly, and the heating time can be reduced. Therefore, if the size of the defect is large and the amount of repair material is large,
This is a particularly effective method. Note that also in this case, the heat treatment is desirably performed in an inert gas atmosphere or in a vacuum to prevent oxidation.

According to a seventh aspect of the present invention, the defective material is covered with the repair material by applying a paste comprising the repair material and an organic binder. This is a repair method for heat-resistant alloy members.

In the present invention, the method of filling and applying a paste composed of an alloy powder and an organic binder to a defective portion requires filling each defect individually, and is not environmentally friendly by using an organic substance. However, this method is a simple method because no large-scale equipment is required, and can improve the yield of materials.

The invention according to claim 8 is characterized in that the repair material is laminated by a thermal spraying method and the repair material is coated on the defective portion. Is the way.

According to the present invention, although the yield of the repair material is worse than that of the above-mentioned paste, the repair material can be simultaneously formed on the entire surface including the defective portion and automation can be performed. It is environmentally friendly because it does not use any other means.

According to a ninth aspect of the present invention, the thermal spraying method is a high-speed gas flame thermal spraying method (HVOF) or a low-pressure plasma thermal spraying method (V
The method for repairing a heat-resistant alloy member according to claim 8, wherein

As the thermal spraying method, plasma spraying in air (A
Low pressure plasma spraying (VPS) and high-speed gas flame spraying (HVO), which can form films with less oxygen content than PS)
F) is preferred. As a pretreatment for such thermal spraying, there is generally a step of roughening the surface to be sprayed. In this case, it is desirable that the surface roughness of the repaired part be 10 μm or less in Ra. This is because the crystal-controlled heat-resistant alloy member is liable to be recrystallized by the heat treatment at the portion deformed by the surface roughening treatment to change the original crystal structure or to be easily polycrystallized. Examples of a method of roughening the surface to be sprayed include a method of performing blasting with a gas pressure reduced to ² kg / cm ² or less, and a method of using glass beads instead of hard alumina as blast powder.

Further, by spraying a cooling gas to the repaired portion in the thermal spraying step, there is an effect that oxidation of the repaired portion and the heat-resistant alloy member can be prevented.

[0030] In the invention according to claim 10, the heating temperature is 1
The method for repairing a heat-resistant alloy member according to any one of claims 3 to 5, wherein the temperature is in a range of 050 ° C to 1250 ° C.

In the eleventh aspect, the heating temperature may be 1
The method for repairing a heat-resistant alloy member according to any one of claims 3 to 5, wherein the temperature is in a range of 100 ° C to 1200 ° C.

By continuing the heat treatment in the range of 1050 ° C. to 1250 ° C. of the present invention, B in the repair material is sufficiently diffused into the heat-resistant alloy member to increase the melting point of the repair material.
The isothermal solidification phenomenon in which solidification proceeds from the diffusion portion proceeds.
By allowing the isothermal solidification phenomenon to proceed sufficiently, solidification proceeds in a state where the crystal structure of the repaired portion is elongated from the crystal structure of the heat-resistant alloy member. If the heating temperature is too high, the melted repair material evaporates and the repair material is reduced. On the other hand, if the heating temperature is too low, there is a problem that the progress of B diffusion slows down. Therefore, the heating temperature is set in the range of 1050 ° C to 1250 ° C, preferably in the range of 1100 ° C to 1200 ° C. preferable. The heating time is determined depending on the relationship with the heating temperature, but is generally from 1 hour to 100 hours. The components of the repair material and the heat-resistant alloy member cause mutual diffusion during these heat treatments, and the combination of the heating temperature and time of the present invention causes the composition of the repair portion and the heat-resistant alloy member to have the same composition. Therefore, the crystal structure and the composition of the heat-resistant alloy member are equivalent.

In the case where an oxide or the like is formed in a defect such as a crack prior to the repair, the oxide is removed mechanically or by a method such as acid cleaning or heat cleaning in hydrogen. It is preferable to include a step of removing the oxide.

According to a twelfth aspect of the present invention, there is provided a high-temperature component repaired by the method for repairing a heat-resistant alloy member according to any one of the third to eleventh aspects.

According to the present invention, it is possible to obtain a high-temperature component made of a heat-resistant alloy in which the repaired portion has properties similar to those of the original heat-resistant alloy member by repairing the defective portion, and the crystal structure of which has been well repaired is controlled. Can be.

According to a thirteenth aspect of the present invention, there is provided a high-temperature component wherein the high-temperature component according to the twelfth aspect is subjected to HIP processing.

In the present invention, by subjecting a high-temperature component obtained by applying the repair method to HIP processing, even if minute voids remain, it is possible to crush and densify. Note that the conditions of the HIP treatment are preferably a temperature of 1200 ° C., a gas pressure of 1700 kgf / cm ² , and a treatment time of 4 hours.

According to a fourteenth aspect of the present invention, the high temperature component is a high temperature component for a gas turbine.
A high-temperature component according to 2 or 13.

In the present invention, it is possible to obtain a high-temperature component which can be applied particularly to a high-temperature component for a gas turbine under severe operating conditions.

According to a fifteenth aspect of the present invention, the high-temperature component repaired by the method for repairing a heat-resistant alloy member has a corrosion-resistant coating layer or a heat-shielding coating layer formed on a surface thereof. Parts.

In the case where the high-temperature component is a high-temperature component for a gas turbine such as a gas turbine blade, after the repair, it includes the repaired surface,
By forming a corrosion-resistant coating layer or a corrosion-resistant coating layer and a heat-shielding coating layer on a wing surface, corrosion resistance and heat-shielding properties can be improved to provide a high-temperature component suitable for high-temperature use. It is appropriate that the coating layer is formed by thermal spraying.

[0042]

DESCRIPTION OF THE PREFERRED EMBODIMENTS A repair material of the present invention, a method for repairing a heat-resistant alloy member using the repair material, and a high-temperature component repaired by this method will be described below with reference to FIGS. I do.

In the present embodiment, a Ni-based single crystal alloy is used as a heat-resistant alloy member, an artificial groove-like defect is provided in the heat-resistant alloy member as a defect portion, and a repair material is penetrated into the groove-like defect to repair. Was done.

The heat-resistant alloy member is made of a Ni-based single crystal alloy, and the approximate composition of this alloy is as follows:
5, Co: 9.0, Mo: 0.6, W: 6.0, Ta:
6.5, Ti: 1.0, Al: 5.5, Re: 3.0,
Hf: 0.1 and the balance being Ni.

FIG. 1 is a diagram showing a cross section of a heat-resistant alloy member. FIG. 1 (a) is a diagram showing a cross-section in which a groove-like defect is formed in a heat-resistant alloy member. FIG. It is a figure showing the section of the heat-resistant alloy member after it did.

As shown in FIG. 1A, the heat-resistant alloy member 1
Is artificially provided with a groove defect 2 having a width of 0.1 mm and a depth of 1 mm. In addition, a groove defect having a width of 0.2 mm and a depth of 2 mm larger than the groove shown in FIG. 1A was artificially provided.

The repaired surface including the groove defect 2 was blasted using alumina powder having a particle size of 50 mesh or less to roughen the surface to Ra: 1 to 10 μm. Thereafter, a repair material powder having a particle diameter of 5 to 50 μm was formed to a thickness of about 0.3 mm by a high-speed gas flame spraying (HVOF) method. The spraying conditions were as follows: the flow velocity was 850 m / sec, and the repair surface temperature was about 150 to
The temperature was set to 200 ° C.

The repair material is a material having the composition shown in Table 1. In the embodiment, the repair material contains Ni as a main component, contains up to 6.0% by weight of Cr, contains 1.0 to 3.5% by weight of B, Sample No. 1 in which the amount of oxygen was less than 0.1% by weight. No. 1 to No. 1 5
Was used. On the other hand, as a comparative example, sample No. 6 to sample N
o. Sample No. 8 was used. Sample No. 6 had a Cr content of 20% by weight, In No. 7, the amount of Cr was added at 15% by weight and the amount of B was added at 4% by weight, so that the amounts added were larger than those of the present invention. In addition, the sample No. In No. 8, the amount of oxygen is out of the range of the present invention, and the amount of oxygen is more than 0.1.

[0049]

[Table 1]

The sample Nos. Of the above Examples and Comparative Examples were used.
1 to Sample No. 8 was sprayed onto the groove defect 2 and then heated in a vacuum of about 5 × 10 ⁻⁵ torr, and the repair material was permeated into the groove defect 2 and repaired.
As shown in (b), the heat-resistant alloy member 1 in which the groove-like defects 2 were repaired with the repair material 3 was obtained.

Thereafter, the cross section of the heat-resistant alloy member 1 was cut and polished, and the repaired state of the groove-like defect 2 was observed and examined by an optical microscope and a scanning electron microscope. As a result, the repair material 3 filled the groove-like defect 2 satisfactorily in each of the repair materials of the example and the comparative example.

FIG. 2 is a view showing the structure of the repaired part of the embodiment. The structure of the repaired part has almost no crystal grain boundaries, and the observation 4 shows that the precipitation 4 of γ 'equivalent to that of the heat-resistant alloy member was observed by an electron microscope. Was done. In particular, in the region with a repair width of about 0.1 mm, isothermal solidification proceeded sufficiently and the crystal structure was equivalent to that of the heat-resistant alloy member 1. When the repair width greatly exceeds 0.1 mm, a long time tends to be required for isothermal solidification. The crystal structure of the isothermally solidified region was investigated by X-ray diffraction. The result is shown in FIG. The horizontal axis indicates the diffraction angle (2θ),
The vertical axis indicates the intensity. As shown in FIG.
Since a peak appears in the vicinity of the degree, only a single crystal plane was detected, indicating that single crystallization was in progress.

On the other hand, when a repairing material different from the repairing material composition of the present invention is used, or when a heat treatment is performed at a temperature exceeding the heating temperature range of the present invention, the repaired part has Many unmatched crystal grain boundaries were generated, and the crystal structure was different from that of the example.

FIG. 4 shows a sample No. of the comparative example. 6 is a view showing a repaired part using the repair material of No. 6;
When it was set to 0%, it was found that many crystal grain boundaries 5 were formed in the repaired portion.

FIG. 5 shows the sample No. of the comparative example. 7 is a view showing a repaired part using the repair material of FIG. 7, and when the B amount of the repair material is set to 4%, as in FIG.
Turned out to be generated.

FIG. 6 shows a sample No. of the comparative example. FIG. 9 is a view showing a structure of a repaired part when a heat treatment is performed at 1280 ° C. using the repair material No. 7; As shown in FIG.
Large cavities 6 were formed in the repaired portion, and it was found that when the heat treatment was performed at a temperature higher than the range of the present invention, the repair material 3 had evaporated from the repaired portion.

According to the present embodiment, by repairing a heat-resistant alloy member with a repair material having a composition falling within the range of the present invention, a microcrystal that prevents a crystal structure due to generation of grain boundaries when the repair material is melted and solidified. Can be prevented, and the solidification behavior of the heat-resistant alloy member with its crystal structure extended can be easily obtained. Therefore, the crystal structure is similar to a heat-resistant alloy member whose crystal structure is controlled, such as a directionally solidified alloy or a single crystal alloy. Can be obtained.

In this embodiment, the groove-like defect 2 is formed in the heat-resistant alloy member 1 and the repair material 4 is sprayed on the groove-like defect 2 for repair. Instead, when the width of the defective portion is large, the part made of the same material as the heat-resistant alloy member 1 is shaped by processing the vicinity of the defective portion, and the part processed into the shape corresponding to the shape is replaced with the defective portion. After the loading, the gap is repaired by the same method as the groove-shaped defect 2 shown in the present embodiment, so that the repair time can be greatly reduced. In addition, by matching the crystal orientations of the two within several degrees, the gap between the two exhibited an isothermal solidification structure similar to that of the groove-like defect 2 and was successfully repaired.

In this embodiment, the surface is roughened to Ra: 1 to 10 μm in the surface roughening step. However, in the surface roughening step, the surface of the Ni-based alloy is sand-blasted by changing the air pressure. When the relationship between the roughness and the deformation of the heat-resistant alloy member was measured, when the surface roughness exceeded 1 μm, remarkable deformation and disorder of the crystal structure were observed particularly as the roughness increased. In the case of a single crystal alloy, polycrystallization was observed by heat treatment. When the air pressure was high, a large amount of the blast powder penetrated the heat-resistant alloy member and was observed. Further, in the thermal spraying step, when a cooling gas was not sprayed on the repaired portion, discoloration due to oxidation of the surface was observed, but no remarkable oxidation which could be visually observed by spraying was not observed.

In the present embodiment, the thermal spraying method is used as a method for coating the repair material in the vicinity of the defect.
A method other than the thermal spraying method can be applied. For example, a paste method can be applied. When the paste method is applied,
Although there was a problem that the degree of vacuum was reduced due to evaporation of organic substances during the vacuum heat treatment, there is an advantage that the amount of the repair material used can be reduced.

Next, when a gas turbine blade is applied as a high-temperature component, a step of adjusting the repaired part to a predetermined component shape by post-processing is performed.
A thermal barrier coating such as a corrosion resistant coating, or a corrosion resistant coating and a partially stabilized zirconia material, was provided. Specifically, high-speed gas flame spraying (HVO)
F) to form a corrosion-resistant coating of NiCoCrAlY alloy of about 0.15 mm, and spray 8% yttria-stabilized zirconia powder by atmospheric plasma spraying (APS) to form a thermal barrier coating layer of about 0.3 mm. Formed.

In the present embodiment, by applying the corrosion-resistant coating and the heat-shielding coating, it is possible to obtain a good gas turbine blade having high heat resistance.

[0063]

As described above, according to the repair material and heat-resistant alloy member method of the present invention, a heat-resistant alloy member having a controlled crystal structure such as a directionally solidified alloy and a single crystal alloy can be repaired. Since the repaired portion has a crystal structure equivalent to that of the heat-resistant alloy member by the repair, the performance of the repair can be improved and a high-temperature component having a longer life can be obtained.

[Brief description of the drawings]

FIGS. 1A and 1B are diagrams illustrating an embodiment of the present invention, in which FIG. 1A is a cross-sectional view of a heat-resistant alloy member provided with groove defects, and FIG. FIG.

FIG. 2 is a diagram illustrating an embodiment of the present invention, and is a diagram illustrating a structure of a repaired part observed by an electron microscope.

FIG. 3 is a diagram illustrating an embodiment of the present invention, and is a diagram illustrating a result of investigating a crystal structure by X-ray diffraction.

FIG. 4 shows a sample N of a comparative example in the embodiment of the present invention.
o. The figure which shows the structure of the repair part using the repair material of No. 6.

FIG. 5 is a sample N of a comparative example in the embodiment of the present invention.
o. The figure which shows the structure of the repair part using the repair material of No. 7.

FIG. 6 shows a sample N of a comparative example in the embodiment of the present invention.
o. The figure which shows the structure of the repair part which performed the heat processing at 1280 degreeC using the repair material of No. 7.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Heat-resistant alloy member 2 Groove defect 3 Repair material 4 Precipitation of γ '5 Crystal grain boundary 6 Cavity

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁷ Identification symbol FI Theme coat ゛ (Reference) C23C 4/12 C23C 4/12 F01D 5/28 F01D 5/28 F02C 7/00 F02C 7/00 CD / / B23K 35/30 340 B23K 35/30 340L C22C 19/05 C22C 19/05 B B23K 103: 16 B23K 103: 16 (72) Inventor Satoshi Asai 2-4 Suehirocho, Tsurumi-ku, Yokohama, Kanagawa Prefecture Toshiba Corporation Inside Keihin Works (72) Inventor Toshiaki Fuse 2-4-4 Suehirocho, Tsurumi-ku, Yokohama-shi, Kanagawa Prefecture Inside Keihin Works, Toshiba Corporation (72) Kazutoshi Nishimoto 1-12-16 Kita-Kasugaoka, Ibaraki-shi, Osaka (72) Invention Person Kazuyuki Saida 5-12-17 Izumi, Taisho-ku, Osaka, Osaka F term (reference) 3G002 AA11 AA13 AB07 AB08 BA06 BA10 BB04 BB05 EA05 EA06 GA10 GB04 4E0 67 AA09 AB05 AD08 BA06 DB03 DC06 EB02 4K031 AA02 AB02 AB06 AB08 BA03 CB22 DA01 DA04 EA10 EA11 FA03 FA06 FA07

Claims (15)

[Claims] 1. A repair material for repairing a defective portion such as a crack or a thinning of a heat-resistant alloy member having a controlled crystal structure, particularly a γ′-reinforced Ni-based alloy member, the repair material comprising:
Ni is a main component, Cr is up to 6.0% by weight, and B is 1.
A repair material characterized by containing 0 to 3.5% by weight. 2. A repair material for repairing a defect such as a crack or a thinning of a heat-resistant alloy member having a controlled crystal structure, particularly a γ′-reinforced Ni-based alloy member, wherein the repair material is:
Ni as a main component, maximum of 5.0% by weight of Cr, and 1.
A repair material containing 5 to 3.0% by weight and oxygen at 0.1% by weight or less. 3. A method for repairing a heat-resistant alloy member having a controlled crystal structure, particularly a defect portion such as a crack or a reduction in thickness of a γ′-reinforced Ni-base heat-resistant alloy member, the method comprising: On the repaired surface with Cr up to 6.0% by weight,
A method for repairing a heat-resistant alloy member, comprising coating a repair material containing 1.0 to 3.5% by weight of B and containing Ni as a main component, followed by heat treatment in an inert atmosphere. 4. A method for repairing a defect of a heat-resistant alloy member having a controlled crystal structure, in particular, a crack or a thinning of a γ′-reinforced Ni-base heat-resistant alloy member, comprising the steps of: On the repaired surface containing Ni as a main component, containing up to 5.0% by weight of Cr and 1.5 to 3.0% by weight of B,
After coating the repair material with oxygen less than 0.1% by weight,
A method for repairing a heat-resistant alloy member, which comprises performing a heat treatment in an inert atmosphere. 5. After loading a part made of a material equivalent to a heat-resistant alloy member and having a shape conforming to the size of the defect part into the defect part, the defect part and the part loaded in the defect part are re-formed. The method for repairing a heat-resistant alloy member according to claim 3 or 4, wherein a repair material is coated on the gap portion, and heat treatment is performed in an inert atmosphere. 6. The repair material according to claim 3, wherein a mixture of an alloy powder having the same composition as the heat-resistant alloy member and the repair material according to claim 3 or 4 is used as the repair material. The method for repairing a heat-resistant alloy member according to item 1. 7. The method for repairing a heat-resistant alloy member according to claim 3, wherein a paste comprising a repair material and an organic binder is applied to cover the repair material on the defective portion. . 8. The method for repairing a heat-resistant alloy member according to claim 3, wherein the repair material is laminated by a thermal spraying method so as to cover the defective portion with the repair material. 9. The thermal spraying method is a high-speed gas flame spraying method (HVO).
The method for repairing a heat-resistant alloy member according to claim 8, wherein the method is F) or low pressure plasma spraying (VPS). 10. The heating temperature is from 1050 ° C. to 1250 ° C.
The method for repairing a heat-resistant alloy member according to any one of claims 3 to 5, wherein the temperature is in the range of ° C. 11. The heating temperature is from 1100 ° C. to 1200
The method for repairing a heat-resistant alloy member according to any one of claims 3 to 5, wherein the temperature is in the range of ° C. 12. A high-temperature component repaired by the method for repairing a heat-resistant alloy member according to claim 3. 13. A high-temperature component, wherein the high-temperature component according to claim 12 is subjected to HIP processing. 14. The high-temperature component according to claim 12, wherein the high-temperature component is a high-temperature component for a gas turbine. 15. The high-temperature component according to claim 11, wherein a corrosion-resistant coating layer or a thermal barrier coating layer is formed on a surface of the high-temperature component repaired by the method for repairing a heat-resistant alloy member.